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RESEARCH PAPERS

Numerical Simulation of the Shock-Tip Leakage Vortex Interaction in a HPC Front Stage

[+] Author and Article Information
M. Hoeger, G. Fritsch, D. Bauer

Daimler-Benz Aerospace, MTU Motoren- und Turbinen-Union München GmbH, Dachauer Straße 665, München, Germany 80995

J. Turbomach 121(3), 456-468 (Jul 01, 1999) (13 pages) doi:10.1115/1.2841338 History: Received February 01, 1998; Online January 29, 2008

Abstract

For a single-stage transonic compressor rig at the TU Darmstadt, three-dimensional viscous simulations are compared to L2F measurements and data from the EGV leading edge instrumentation to demonstrate the predictive capability of the Navier–Stokes code TRACE_S. In a second step the separated regions at the blade tip are investigated in detail to gain insight into the mechanisms of tip leakage vortex-shock interaction at operating points close to stall, peak efficiency, and choke. At the casing the simulations reveal a region with axially reversed flow, leading to a rotationally asymmetric displacement of the outermost stream surface and a localized additional pitch-averaged blockage of approximately 2 percent. Loss mechanisms and streamline patterns deduced from the simulation are also discussed. Although the flow is essentially three-dimensional, a simple model for local blockage from tip leakage is demonstrated to significantly improve two-dimensional simulations on S1-surfaces.

Copyright © 1999 by The American Society of Mechanical Engineers
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